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公开(公告)号：US20220097864A1
公开(公告)日：2022-03-31
申请号：US17471774
申请日：2021-09-10
Applicant: GE Avio S.r.l.
Inventor： Mehdi M. Baladi , Aniello Esposito , Sridhar Adibhatla , Kathleen K. Collins
Abstract: A system and method for optimizing performance of an aircraft or boat through detection and trending of engine deterioration based on the performance of the vehicle's gas turbine. The system and method detects declines in engine power due to either of in-transit events or over the extended lifetime of the engine, the declines being due to routine engine part aging or an event. As engine power gradually or suddenly deteriorates, the system and method lowers a maximum operating line which defines the safe limits for peak engine power consumption during flight. For in-transit events, the system and method detects when actual power consumption is approaching the current maximum operating line. The controller may then automate changes to operations of entirely separate aircraft systems, such as rebalancing electrical energy consumption by various non-engine elements of the aircraft.
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Patent Agency Ranking
公开(公告)号：US12291344B2
公开(公告)日：2025-05-06
申请号：US18410493
申请日：2024-01-11
Applicant: GE Avio S.r.l.
Inventor： Mehdi M. Baladi , Aniello Esposito , Sridhar Adibhatla , Kathleen K. Collins
Abstract: A system and method for optimizing performance of an aircraft or boat through detection and trending of engine deterioration based on the performance of the vehicle's gas turbine. The system and method detects declines in engine power due to either of in-transit events or over the extended lifetime of the engine, the declines being due to routine engine part aging or an event. As engine power gradually or suddenly deteriorates, the system and method lowers a maximum operating line which defines the safe limits for peak engine power consumption during flight. For in-transit events, the system and method detects when actual power consumption is approaching the current maximum operating line. The controller may then automate changes to operations of entirely separate aircraft systems, such as rebalancing electrical energy consumption by various non-engine elements of the aircraft.
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公开(公告)号：US12123359B2
公开(公告)日：2024-10-22
申请号：US15978097
申请日：2018-05-12
Applicant: GE Avio S.r.l.
Inventor： Mehdi Milani Baladi , Robert Jon McQuiston , Aniello Esposito , Joseph Donofrio , Nicholas William Simone , Simone Castellani
CPC classification number: F02C9/18 , F02C6/08 , F04D27/0215 , F05D2220/323 , F05D2260/606 , F05D2270/101 , F05D2270/30
Abstract: An aircraft can comprise an engine, an environmental control system, an engine controller, and a plurality of sensors detecting engine or aircraft parameters. Engine or aircraft operation can be updated in real time based on input from the sensors, including airflow management or operation parameters.
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公开(公告)号：US20240208660A1
公开(公告)日：2024-06-27
申请号：US18410493
申请日：2024-01-11
Applicant: GE Avio S.r.l.
Inventor： Mehdi M. Baladi , Aniello Esposito , Sridhar Adibhatla , Kathleen K. Collins
CPC classification number: B64D31/06 , B64D33/02 , B64D45/00 , F02C9/00 , G08G5/003 , B64D2033/0273 , B64D2221/00
Abstract: A system and method for optimizing performance of an aircraft or boat through detection and trending of engine deterioration based on the performance of the vehicle's gas turbine.
The system and method detects declines in engine power due to either of in-transit events or over the extended lifetime of the engine, the declines being due to routine engine part aging or an event. As engine power gradually or suddenly deteriorates, the system and method lowers a maximum operating line which defines the safe limits for peak engine power consumption during flight. For in-transit events, the system and method detects when actual power consumption is approaching the current maximum operating line. The controller may then automate changes to operations of entirely separate aircraft systems, such as rebalancing electrical energy consumption by various non-engine elements of the aircraft.-
公开(公告)号：US11434830B2
公开(公告)日：2022-09-06
申请号：US17054682
申请日：2019-06-18
Applicant: GE Avio S.r.l.
Inventor： Aniello Esposito , Giuseppe Donini
Abstract: A control system (50) for a turbopropeller engine (2) of an aircraft (1) having a gas turbine (11) and a propeller assembly (3) coupled to the gas turbine (11), the gas turbine (11) having a compressor (12) coupled to an air intake (13) and a temperature sensor (22) being arranged in the air intake (13) to measure the temperature of engine intake air and provide a sensed temperature (T1sens); the control system envisages: a compensation system (40) to receive the sensed temperature (T1sens) from the temperature sensor (22) and to add to the sensed temperature (T1sens) a compensation quantity (comp) to compensate for a delay introduced by the time constant (τ) of the temperature sensor (22) and generate a compensated temperature (T1comp); and a control unit (20) to perform engine control operations based on the compensated temperature (T1comp). In particular, the compensation quantity (comp) is calculated based on an ISA International Standard Atmosphere—temperature (T1ISA), which is determined as a function of an external pressure (P0) measured by a pressure sensor (35).
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公开(公告)号：US20210102501A1
公开(公告)日：2021-04-08
申请号：US17054682
申请日：2019-06-18
Applicant: GE Avio S.r.l.
Inventor： Aniello Esposito , Giuseppe Donini
IPC: F02C9/20
Abstract: A control system (50) for a turbopropeller engine (2) of an aircraft (1) having a gas turbine (11) and a propeller assembly (3) coupled to the gas turbine (11), the gas turbine (11) having a compressor (12) coupled to an air intake (13) and a temperature sensor (22) being arranged in the air intake (13) to measure the temperature of engine intake air and provide a sensed temperature (T1sens); the control system envisages: a compensation system (40) to receive the sensed temperature (T1sens) from the temperature sensor (22) and to add to the sensed temperature (T1sens) a compensation quantity (comp) to compensate for a delay introduced by the time constant (τ) of the temperature sensor (22) and generate a compensated temperature (T1comp); and a control unit (20) to perform engine control operations based on the compensated temperature (T1comp). In particular, the compensation quantity (comp) is calculated based on an ISA International Standard Atmosphere—temperature (T1ISA), which is determined as a function of an external pressure (P0) measured by a pressure sensor (35).
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